Raceway systems and methods for routing transferring components within an interior cabin of an aircraft

ABSTRACT

A raceway system and method within an internal cabin of an aircraft include a plurality of routing modules that are coupled together. Each of the plurality of routing modules includes a main housing that routes one or more transferring components to one or more monuments within the internal cabin. A raceway system and method for an aircraft includes a transferring component attachment system that includes a plurality of transferring component support struts, and one or more transferring components coupled to the plurality of transferring component support struts.

FIELD OF THE DISCLOSURE

Embodiments of the present disclosure generally relate to racewaysystems and methods for routing transferring components (such aselectrical wiring, ducting, liquid conduits, and/or the like) within aninterior cabin of an aircraft.

BACKGROUND OF THE DISCLOSURE

Certain military commercial derivate aircraft (MCDA) such as airbornewarning and control system (AWACS), joint surveillance and target attackradar system (JSTARS), P-8 Maritime Patrol Aircraft, KC-46 Tanker, andthe like are manufactured based on commercial airframes. Such MCDAinclude various systems, sub-systems, and transferring components (thatis, components that transfer an electrical signal or fluid such as airor liquid) beyond that which are typically found in commercial aircraft.For example, during a manufacturing process of a military commercialderivate aircraft, mission system wiring, environmental cooling ducts,aerial refueling tubes, liquid cooling lines, and the like are securedto various portions of a fuselage, for example.

As can be appreciated, engineering effort associated with the design ofcompliant installations for the various systems within the aircraft isrigorous as a result of multiple routing paths to meet requirements andavoid existing systems and structures. Each new routing path increasesboth the engineering design effort and manufacturing factory labor hoursassociated with installing structural support provisions at primarystructures. The design considerations for installation of variousmilitary systems, sub-systems, and transferring components within acommercial airframe is unique for each aircraft and typically requiressubstantial engineering effort to define routing paths around existingcommercial systems, and generate associated installation, assembly, anddetail drawings for all required support provisions. Moreover, themanufacturing effort is also labor intensive in that individualstypically individually secure each transferring component to frames viasupport provisions and fasteners, for example.

In general, a fuselage of an aircraft includes numerous frames coupledto stringers that extend along a length of the fuselage. In order tosecurely mount transferring components (such as wiring, air ducts,liquid conduits, and the like) within an internal cabin formed by thefuselage, the transferring components are secured to portions of theframes and the stringers with fasteners, such as clips. As such, complexengineering is needed to determine thousands of attachment points. Afterthe transferring components are secured to the frames and stringers,wall structures may be secured over the frames and stringers. That is,the transferring components are secured to frames and stringers thatform sidewall portions, ceilings, and the like within the internalcabin. When sidewalls and other interior finishing components areinstalled, they cover up various transferring components, therebyreducing access to such transferring components. Accordingly, gainingaccess to such transferring components for maintenance, replacement, andthe like may be time and labor intensive, as well as expensive.

SUMMARY OF THE DISCLOSURE

A need exists for a system and a method for efficiently mountingtransferring components (such as electrical wiring, ducting, liquidconduits, and/or the like) within an internal cabin of an aircraft, suchas a military commercial derivative aircraft. Further, a need exists fora system and a method that reduce the time, effort, and cost of securingtransferring components within an internal cabin of an aircraft, andreduce a total manufacturing time. Further, a need exists for a systemand method of efficiently modifying current routing systems.Additionally, due to certain regulations (such as United States FederalAviation Administration Electrical Wiring Interconnect Systemregulations), a need exists for systems and methods that allow for easyand cost-efficient inspection of installed wiring.

With those needs in mind, certain embodiments of the present disclosureprovide a raceway system within an internal cabin of an aircraft. Theraceway system includes a plurality of routing modules that are coupledtogether. Each of the plurality of routing modules includes a mainhousing that routes one or more transferring components to one or moremonuments within the internal cabin.

In at least one embodiment, the main housing includes a bottom opening.Portions of the one or more transferring components extend through thebottom opening to couple to the monument(s).

At least one of the plurality of modules may include a door that ispivotally coupled to the main housing proximate to the bottom opening.The door is configured to be selectively moved between an open positionand a closed position.

In at least one embodiment, at least one fixed panel extends between atleast one of the plurality of modules and the monument(s).

The plurality of routing modules are outside of a sidewall and ceilingof the internal cabin. At least one of the plurality of routing modulesis positioned above the monument(s).

In at least one embodiment, each of the plurality of routing modules issecured to one or both of at least one frame or at least one stringer byone or more stowage bin mounting supports.

In at least one embodiment, one or more of the plurality of routingmodules comprises a longitudinal separating wall that defines a firstspace and a second space. The first space and the second space allowdifferent transferring components to be separated from one another, suchas may be required by aircraft design practices and regulations.

In at least one embodiment, each of the plurality of routing modulesincludes one or more transferring component support struts that securethe transferring component(s) within the main housing. The transferringcomponent strut(s) are secured to one or more lugs within the mainhousing through one or more fasteners. The transferring component(s) maybe secured to the transferring component support strut(s) before beingsecured within the main housing.

At least one of the plurality of routing modules may include a topopening formed through a top wall.

Certain embodiments of the present disclosure provide a raceway methodfor an internal cabin and/or lower lobes (such as underneath a floor) ofan aircraft. The raceway method includes providing a plurality ofrouting modules, coupling the plurality of routing modules togetherwithin the internal cabin, and routing one or more transferringcomponents to one or more structures (such as monuments) within theinternal cabin through main housings of the plurality of routingmodules.

In at least one embodiment, the raceway method includes extendingportions of the one or more transferring components through bottomopenings of the main housings, and disposing the plurality of routingmodules outside of a sidewall and ceiling of the internal cabin.

In at least one embodiment, the raceway method includes positioning atleast one of the plurality of routing modules above the one or moremonuments.

In at least one embodiment, the raceway method also includes securingeach of the plurality of routing modules to one or both of at least oneframe or at least one stringer with one or more existing stowage binmounting supports.

In at least one embodiment, the providing includes providing the one ormore of the plurality of routing modules with a longitudinal separatingwall that defines a first space and a second space. The first space andthe second space allow different transferring components to be separatedfrom one another.

In at least one embodiment, the raceway method includes securing the oneor more transferring components to one or more transferring componentstruts, and securing the one or more transferring component struts thatare coupled to the one or more transferring components to one or morelugs within the main housings.

The providing may also include forming a top opening through a top wallof at least one of the plurality of routing modules.

Certain embodiments of the present disclosure provide an aircraftincluding a fuselage defining an internal cabin. The fuselage includes aplurality of frames and a plurality of stringers connected to theplurality of frames. One or more monuments are within the internalcabin. A raceway system is within the internal cabin. The raceway systemincludes a plurality of routing modules that are coupled together, asdescribed herein.

Certain embodiments of the present disclosure provide a raceway systemfor an aircraft. The raceway system includes a transferring componentattachment system that includes a plurality of transferring componentsupport struts, and one or more transferring components coupled to theplurality of transferring component support struts.

In at least one embodiment, each of the plurality of transferringcomponent support struts includes a main beam having ends that areconfigured to couple to securing lugs of a main housing of a routingmodule. For example, each of the ends may include prongs separated by aspace.

The transferring component(s) are coupled to one or more of topsurfaces, bottom surfaces, or through the plurality of transferringcomponent support struts. As an example, a first transferring componentis coupled to top surfaces of the plurality of transferring componentsupport struts, and a second transferring component is coupled to bottomsurfaces of the plurality of transferring component support struts.

In at least one embodiment, each of the plurality of transferringcomponent support struts includes one or more securing clips thatretains one or more portions of the transferring component(s).

In at least one embodiment, the plurality of transferring componentsupport struts and the transferring component(s) are wound onto a drumreel.

In at least one embodiment, the raceway system also includes a pluralityof routing modules that are coupled together. The transferring componentattachment system is coupled to the plurality of routing modules. Theplurality of routing modules include main housings that are configuredto route the one or more transferring components to one or moremonuments within the aircraft. In at least one embodiment, the pluralityof routing modules are outside of a sidewall and ceiling of an internalcabin of the aircraft. Each of the plurality of routing modules may besecured to one or both of at least one frame or at least one stringer byone or more stowage bin mounting supports.

Certain embodiments of the present disclosure provide a raceway methodfor an aircraft. The raceway method includes forming a transferringcomponent attachment system. The forming the transferring componentattachment system includes providing a plurality of transferringcomponent support struts, and coupling one or more transferringcomponents to the plurality of transferring component support struts.

In at least one embodiment, the coupling includes coupling thetransferring component(s) to one or more of top surfaces, bottomsurfaces, or through the plurality of transferring component supportstruts. For example, the coupling includes coupling a first transferringcomponent to top surfaces of the plurality of transferring componentsupport struts, and coupling a second transferring component to bottomsurfaces of the plurality of transferring component support struts.

The raceway method may include retaining one or more portions of thetransferring component(s) by one or more securing clips of the pluralityof transferring component support struts.

The raceway method may include winding the transferring component systemonto a drum reel.

In at least one embodiment, the raceway method includes coupling aplurality of routing modules that together, and coupling thetransferring component attachment system to the plurality of routingmodules. The raceway method may include disposing the plurality ofrouting modules outside of a sidewall and ceiling of an internal cabinof the aircraft. The raceway method may include securing each of theplurality of routing modules to one or both of at least one frame or atleast one stringer by one or more stowage bin mounting supports.

Certain embodiments of the present disclosure provide a raceway methodfor an aircraft. The raceway method includes coupling one or moretransferring components to a plurality of support struts to form atransferring component attachment system, winding the transferringcomponent attachment system onto a drum reel, unrolling the transferringcomponent attachment system off of the drum reel, and securing thetransferring component attachment system to a plurality of routingmodules within the aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 illustrates a perspective top view of an aircraft, according toan embodiment of the present disclosure.

FIG. 2 illustrates a perspective view of a raceway system within aninternal cabin of the aircraft, according to embodiment of the presentdisclosure.

FIG. 3 illustrates an end view of the raceway system within the internalcabin.

FIG. 4 illustrates a perspective end view of the raceway system withinthe internal cabin.

FIG. 5 illustrates a perspective top view of the raceway system withinthe internal cabin.

FIG. 6 illustrates an end view of the raceway system.

FIG. 7 illustrates a perspective front view of a drum reel having firsttransferring components wound therearound, according to an embodiment ofthe present disclosure.

FIG. 8 illustrates a flow chart of a method of securing transferringcomponents within the internal cabin of the aircraft, according to anembodiment of the present disclosure.

FIG. 9 illustrates a perspective top view of a plurality of transferringcomponents coupled to a plurality transferring component support struts,according to an embodiment of the present disclosure.

FIG. 10 illustrates a perspective end view of the plurality oftransferring components coupled to a transferring component supportstrut, according to an embodiment of the present disclosure.

FIG. 11 illustrates a flow chart of a method of securing transferringcomponents within the internal cabin of the aircraft, according to anembodiment of the present disclosure.

DETAILED DESCRIPTION OF THE DISCLOSURE

The foregoing summary, as well as the following detailed description ofcertain embodiments will be better understood when read in conjunctionwith the appended drawings. As used herein, an element or step recitedin the singular and preceded by the word “a” or “an” should beunderstood as not necessarily excluding the plural of the elements orsteps. Further, references to “one embodiment” are not intended to beinterpreted as excluding the existence of additional embodiments thatalso incorporate the recited features. Moreover, unless explicitlystated to the contrary, embodiments “comprising” or “having” an elementor a plurality of elements having a particular condition may includeadditional elements not having that condition.

Certain embodiments of the present disclosure provide a raceway systemfor routing transferring components within an interior cabin of anaircraft. Transferring components transfer signals or fluid betweendifferent systems, structures, or the like. For example, an electricalwire is a component that transfers electrical signals. An air duct is acomponent that transfers a fluid, such as air. A liquid conduit is acomponent that transfers a fluid, such as water or fuel.

In at least one embodiment, the raceway system includes a plurality ofrouting modules that couple together. The raceway system providesflexible and scalable installation of transferring components within theinterior cabin. The routing modules provide defined, simple pathways forcomponent routing and support. In at least one embodiment, each routingmodule is configured to attach to existing commercial aircraft stowagebin support mounting couplers, thereby reducing manufacturing time andeffort due to a reduction in modifications to the airframe. The designhours and manufacturing installation time for support provisions andtransport element installations is greatly reduced, correlating to lowernon-recurring engineering and recurring factory labor costs.

Embodiments of the present disclosure provide raceway systems andmethods that allow convenient access to mission system wiring toaccommodate certain electrical wiring interconnect system (EWIS)inspections throughout the life of an aircraft. The raceway systems andmethods result in lower engineering costs resulting from a pre-definedsubsystem transport element routing volume and lower factory labor costsdue to less time installing the transport elements and supports. Theraceway systems and methods greatly reduce the number of supportprovisions, such as brackets and clamps, which are designed andinstalled to primary structure on each modified aircraft. In at leastone embodiment, the routing modules attach to existing stowage binmounting provisions, such as via bolts, pins, and tie-rods. The racewaysystems and methods reduce engineering development time by allowing fora greater emphasis on subsystem routing within a large, reserved volumecontaining defined pathways to reduce the engineering effort associatedwith routing installations from one point to another on the aircraft.

In at least one embodiment, the raceway systems also segregate missionsystem transferring components, such as within the routing modules for amilitary commercial derivative aircraft from the type certifiedaircraft. By segregating the mission system transferring components inthe module, there is clear demarcation between certified aircraftsystems and mission system transferring components, for example. Therouting modules provide defined space allocations for mechanicalsubsystems such as ducts and tubes as well as for different wire typebased on categorization such as classified, fiber-optic, coax, or powerwiring. Wire separation and location within the volume of the routingmodules may be predefined and consistent across a length of the racewaysystem to simplify wire routing design.

In at least one embodiment, installation of prefabricated and testedwire-groups is expedited through the use of a drum to roll out theassembled wire-group and pin it in place in the raceway system, therebygreatly reducing one of the most labor-intensive manufacturing jobsduring a traditional modification and installation program.

FIG. 1 illustrates a perspective top view of an aircraft 100, accordingto an embodiment of the present disclosure. In at least one embodiment,the aircraft 100 is a military commercial derivate aircraft. In at leastone other embodiment, the aircraft 100 is a commercial aircraft. Theaircraft 100 includes a propulsion system 112 that includes two turbofanengines 114, for example. Optionally, the propulsion system 112 mayinclude more engines 114 than shown. The engines 114 are carried bywings 116 of the aircraft 100. In other embodiments, the engines 114 maybe carried by a fuselage 118 and/or an empennage 120. The empennage 120may also support horizontal stabilizers 122 and a vertical stabilizer124. The fuselage 118 of the aircraft 100 defines an internal cabin 130,which includes a cockpit. The aircraft 100 may be sized, shaped, andconfigured other than shown in FIG. 1. For example, the aircraft 100 maybe a non-fixed wing aircraft.

FIG. 2 illustrates a perspective view of a raceway system 200 within theinternal cabin 130 of the aircraft 100, according to embodiment of thepresent disclosure. The internal cabin 130 includes a floor 202, asidewall 204, and a ceiling 206. Various systems and monuments 208 (suchas cabinets, consoles, computer workstations, and the like) aresupported on the floor 202, underneath the floor 202, suspended over thefloor 202, and/or the like. The internal cabin 130 refers to allinternal portions of an aircraft that are within a space defined by afuselage for example. For example, the internal cabin 130 includes spacewithin the aircraft for individuals, as well as lower lobes, cargoareas, and/or the like.

In at least one embodiment, the raceway system 200 includes a pluralityof routing modules 210. Each routing module 210 includes a main housing212. The main housing 212 includes a bottom opening 214. A door 216 maypivotally couple to the main housing 212 proximate to the bottom opening214, and is configured to be selectively moved between open and closedpositions. In the open position, the bottom opening 214 is exposed andopen. In the closed position, the bottom opening 214 is closed. Asanother option, a fixed panel 218 may extend between a main housing 212and a monument 208.

As shown, the raceway system 200 is outside of the sidewall 204 and theceiling 206. The raceway system 200 is configured to route transferringcomponents to the monuments 208. Because the raceway system 200 is abovethe monuments 208 and not within the sidewall 204 or the ceiling 206,the transferring components routed through the raceway system 200 may beeasily accessed without moving the monuments 208 and/or portions of thesidewall 204 in order to gain access to transport elements.

FIG. 3 illustrates an end view of the raceway system 200 within theinternal cabin 130. In at least one embodiment, the internal cabin 130is formed by a plurality of annular frames 230 and a plurality ofstringers 232 that extend along a length of the internal cabin 130. Forclarity, external portions of the fuselage 118 are not shown in FIG. 3.The ceiling 206 may include a liner 207 that extends between upperportions of the main housings 212 of the routing modules 210.

Each routing module 210 may have an axial cross-section that is the samesize or similar to a stowage bin that may be positioned within acommercial aircraft (but may not be within the military commercialderived aircraft 100). Further, the overall size of each routing module210 may be the same or similar to that of a stowage bin. In this manner,the routing modules 210 may be quickly and efficiently secured toportions of the aircraft 100, such as the frames 230 and the stringers232, using mounting supports 234 that would otherwise be used tosecurely mount stowage bins within the internal cabin 130. In at leastone embodiment, the main housings 212 of the routing modules 210 aresecured to the frames 230 and the stringers 232 with the mountingsupports 234 (such as existing commercial aircraft mounting supports,for example), such as may include support tie rods, which wouldotherwise be used to secure a stowage bin to a frame or stringer. Theraceway systems 200 may occupy existing overhead stowage bin spacewithin the aircraft 100 (which would otherwise be occupied by stowagebins) to route various transferring components, such as wiring and airducts.

The routing modules 210 are not stowage bins. Indeed, a stowage binhaving an exposed bottom opening would not be capable of retainingcarry-on bags. Further, stowage bins have fore and aft walls that wouldprevent transfer components from extending along a length of an aircraftbetween different systems, structures, and the like.

As shown, the routing modules 210 may include open fore and aft ends236. Accordingly, when adjacent routing modules 210 are connectedtogether in an end-to-end fashion, a routing channel 238 is definedtherebetween.

In at least one embodiment, the routing modules 210 include longitudinalseparating walls 240 that separate internal volumes into a first space242 and a second space 244. The separated spaces 242 and 244 allow fordifferent transferring components to be separated or segregated from oneanother. For example, first transferring components 246 (such aselectrical wiring) may extend through the first space 242, while secondtransferring components 248 (such as an air duct) may extend through thesecond space 244. The transferring components 246 may pass out of thebottom opening 214 to couple to a monument 208, such as a mission systemor sub-system. In at least one embodiment, a door 216 includes openingsthat allow the first transferring components 246 to extend through thedoor 216 in the closed position.

As noted, the raceway system 200 routes the first transferringcomponents 246 and the second transferring components 248 along a lengthof the internal cabin 130 to various locations (such as to variousmonuments 208). The raceway systems 200 are outside of the sidewalls 204and the ceiling 206, above the monuments 208, thereby allowing for easyaccess to the first transferring components 246 and the secondtransferring components 248 (in contrast to if the transferringcomponents were within the sidewalls 204, which would typically requirethe monuments 208 to be moved and portions of the sidewalls 204 to beremoved in order to gain access to the transferring components).

FIG. 4 illustrates a perspective end view of the raceway system 200within the internal cabin 130. The separating wall 240 separates thefirst space 242 from the second space 244. Each routing module 210 maybe as long as a typical stowage bin. In at least one other embodiment,each routing module 210 may be longer or shorter than a typical stowagebin. In at least one embodiment, the raceway system 200 may include asingle routing module 210 that extends along a length of the internalcabin 130.

As an option, a fixed panel 218 extends downwardly from a front loweredge 211 of the main housing 212 to a top of a monument 208. In thismanner, the fixed panel 218 provides a closeout that hides and protectsthe first transferring components 246 (for example, electrical wiring orcables) that extend downwardly through the bottom opening 214 and to themonument 208. The fixed panel 218 may be secured to the front lower edge211 and the monument 208 through fasteners.

The routing modules 210 includes a top wall 250 that connects to a frontwall 252, which may include outwardly angled segments. The separatingwall 240 extends downwardly from an internal surface 251 of the top wall250 towards the bottom opening 214. The separating wall 240 may beperpendicular to the top wall 250. In at least one embodiment, therouting modules 210 may include one or more additional separating wallsto provide additional segregated spaces.

First transferring component support struts 260 extend between theseparating wall 240 and the front wall 252. Second transferringcomponent support struts 262 may extend between the top wall 250 and thefront wall 252. Each transferring component support strut 260 and 262includes a main beam 264 having ends 266 and 268 that couple to securinglugs 270 secured to interior surfaces of the main housing 212. Forexample, the ends 266 and 268 securely connect to the securing lugs 270through fasteners, such as pins, bolts, screws, clips, or the like. Thetransferring component struts 260 and 262 provide support ledges for thetransferring components within the routing modules 210. For example, thetransferring components are secured to the struts 260 and/or 262, suchas via clips. The transferring components extend between the struts 260and/or 262. Additionally, the transferring component support struts 260and 262 provide bracing supports within the routing modules 210.Optionally, the routing modules 210 may include more or less supportstruts than shown. For example, the routing modules 210 may include thesupport struts 260, but not the support struts 262, or vice versa.

In at least one embodiment, the support struts 260 and 262 areconfigured to support transferring components (such as wiring) on topand bottom surfaces. The transferring components may be secured to topand bottom surfaces of the support struts 260 and 262 through reciprocalchannels, adhesives, fasteners (such as pins and ties), and/or the like.

FIG. 5 illustrates a perspective top view of the raceway system 200within the internal cabin 130. FIG. 6 illustrates an end view of theraceway system 200. Referring to FIGS. 5 and 6, the routing modules 210are secured to the frames 230 and/or the stringers 232 (shown in FIG. 3)through the mounting supports 234. The mounting supports 234 may includetie rods, brackets, fasteners, and/or the like that are typically usedto mount stowage bins to the frames 230 and/or the stringers 232. Assuch, in at least one embodiment, the mounting supports 234 are stowagebin mounting supports 234 that secure the raceway system 200 to theframes 230 and/or the stringers 232. The mounting supports 234 maysecure to the frames 230 and/or stringers 232 and lugs 270 of therouting modules 210 to secure the raceway system 200 within the internalcabin 130.

As shown in FIG. 6, the second transferring component 248 (such as aduct) is securely mounted to the separating wall 240 via a bracket 249.The bracket 249 extends from an outer surface 243 of the separating wall240 that is opposite from the internal surface 245 on which a lug 270 issecured.

In at least one embodiment, the top walls 250 include top openings 257(as shown in FIG. 5). The top openings 257 allow for transferringcomponents (such as electrical wiring) to pass from internal portions ofthe routing modules 210 to an upper portion of the internal cabin 130.For example, the routing modules 210 may route electrical wiring orcabling to an antenna positioned above the raceway system 200.Optionally, at least some of the routing modules 210 may not include thetop openings 257.

FIG. 7 illustrates a perspective front view of a drum reel 300 havingthe first transferring components 246 (such as electrical wiring) woundtherearound, according to an embodiment of the present disclosure.Referring to FIGS. 4, 6, and 7, in at least one embodiment, the supportstruts 260 and 262 are secured to the first transferring components 246(such as electrical wiring) prior to assembly within the routing modules210. In this manner, the first transferring components 246 are initiallycoupled to the support struts 260 and 262 and wound onto the drum reel300. During an assembly process, the first transferring components 246and the support struts 260 and/or 262 secured thereto are unrolled offof the drum reel 300. The unrolled first transferring components 246 arethen efficiently secured within the routing modules 210 by simplysecuring the support struts 260 and/or 262 to the securing lugs 270,which provides an assembly process that is far more efficient thanindividually securing the first transferring components 246 to frames230 and/or stringers 232 with numerous individual fasteners.

FIG. 8 illustrates a flow chart of a method of securing transferringcomponents (such as electrical wiring or cables) within the internalcabin of the aircraft, according to an embodiment of the presentdisclosure. Referring to FIGS. 1-8, at 400, routing modules 210 areprovided. Each routing module 210 may be sized and shaped the same. Therouting modules 210 are configured to modularly connect together to forma raceway system 200 of a desired length.

At 402, the routing modules 210 are coupled together to form the racewaysystem 200. At 406, the support struts 260 (or 262) are secured to thetransferring components (such as the first transferring components 246),such as through clips, ties, or the like. In at least one embodiment, at408, the transferring components and the coupled support struts arewound onto and around the drum reel 300. For example, a supplier maywind the transferring components and support struts onto the drum reel300. The drum reel 300 is delivered to a customer, such as an aircraftmanufacturer. At 410, the customer unwinds the transferring componentsand coupled support struts from the drum reel 300. Steps 406-410 mayoccur before, after or concurrently with one or more of steps 400-402.At 412, the support struts are coupled to the lugs 270 of the routingmodules 210 (such as via fasteners), thereby securing the transferringcomponents to the raceway system 200. In at least one embodiment, themethod may not include 408-410. In at least one embodiment, subsequentto or during 412, the method may also include securing he raceway system200 to existing mounting structures (such as the mounting supports 234)within the internal cabin 130.

FIG. 9 illustrates a perspective top view of a plurality of transferringcomponents 500 coupled to a plurality transferring component supportstruts 502, according to an embodiment of the present disclosure. FIG.10 illustrates a perspective end view of the plurality of transferringcomponents 500 coupled to a transferring component support strut 502,according to an embodiment of the present disclosure. The transferringcomponents 500 coupled to the transferring component support struts 502form a transferring component attachment system 501.

Each transferring component support strut 502 includes a main beam 504having ends 506 and 508 that are configured to couple to securing lugs(such as the securing lugs 270 shown in FIG. 4) that are secured tointerior surfaces of a main housing (such as the main housing 212 shownin FIG. 4). For example, the ends 506 and 508 include prongs 520separated by a space 522. At least a portion of a securing lug may bepositioned within the space 522, and secured to the prongs 520 viafasteners, such as pins, bolts, screws, clips, or the like. Thetransferring components 500 may be secured to top surfaces 530 andbottom surfaces 532 of the transferring component support struts 502through fasteners, adhesives, and/or the like to form the transferringcomponent attachment system 501. For example, one or more securing clips534 may be secured to a top surface 530 of the main beam 504, and one ormore securing clips 536 may be secured to the bottom surface 532 of themain beam 504. The clips 534 and 536 may be integrally formed with themain beam 504, or may be secured thereto with fasteners, adhesives,and/or the like. Each securing clip 534 and 536 may be include a channel538 that is sized and shaped to conform to a portion of an outer surfaceof a transferring component 500. As such, the securing clips 534 and 536may receive and securely retain portions of the transferring components500 through an interference fit, a clamping fit, and/or the like. In atleast one embodiment, the transferring components 500 may be secured tothe transferring component support struts 502 through adhesives, ties,and/or the like. The transferring component struts 502 provide supportsurfaces (whether on top or below) for the transferring componentswithin routing modules (such as the routing modules 210, shown in FIG.4). For example, referring to FIGS. 4, 9, and 10, the transferringcomponents 500 are secured to the support struts 502, such as via thesecuring clips 534 and 536. The transferring components 500 extend along(such as over and/or under) adjacent support struts 302. In at least oneembodiment, the support struts 302 may include interior channels thatallow the transferring components 500 to pass through the main beams504. Additionally, the transferring component support struts 502 providebracing supports within the routing modules 510.

As noted, the support struts 502 are configured to support transferringcomponents (such as wiring) on the top surfaces 530 and the bottomsurfaces 542 to form the transferring component attachment system 501.Alternatively, the support struts 502 may be configured to supporttransferring components on only the top surfaces 530 or only the bottomsurfaces 502. In at least one other embodiment, the support struts 502are configured to support transferring components through channelsformed through the main beams 504. As such, the support struts 502 maybe configured to support transferring components on top surfaces 530,bottom surfaces 502, and/or through main beams 504 (such as throughchannels or passages formed through the main beams) 504).

Referring to FIGS. 4, 7, 9, and 10, the support struts 502 are securedto the transferring components 500 (such as electrical wiring) to formthe transferring component attachment system 501 prior to assemblywithin the routing modules 210. In this manner, the transferringcomponents 500 are initially coupled to the support struts 502 to formthe transferring component attachment system 501, which is wound ontothe drum reel 300. Optionally, the transferring component attachmentsystem 501 is not wound onto a drum reel. During an assembly process,the transferring component attachment system 501 including thetransferring components 500 (such as the first transferring components246) and the support struts 502 secured thereto, is unrolled off of thedrum reel 300. The unrolled transferring component attachment system 501including the transferring components 500 is then efficiently securedwithin the routing modules 210 by simply securing the support struts 502to the securing lugs 270, which provides an assembly process that is farmore efficient than individually securing the transferring components500 to frames 230 and/or stringers 232 (shown in FIG. 3, for example)with numerous individual fasteners.

In at least one embodiment, the support struts 502 are secured to thetransferring components 500, such as through clips, ties, or the like,to form the transferring component attachment system 501. Thetransferring component attachment system 501 is wound onto and aroundthe drum reel 300. For example, a supplier may wind the transferringcomponent attachment system 501 onto the drum reel 300. The drum reel300 is delivered to a customer, such as an aircraft manufacturer. Thecustomer unwinds the transferring component attachment system 501 fromthe drum reel 300.

FIG. 11 illustrates a flow chart of a method of securing transferringcomponents within the internal cabin of the aircraft, according to anembodiment of the present disclosure. At 600, one or more transferringcomponents are coupled to a plurality of support struts to form atransferring component attachment system. At 602, the transferringcomponent attachment system is wound onto a drum reel. At 604, thetransferring component attachment system is unrolled off of the drumreel. Optionally, the method may not include 602 and 604. At 606, thetransferring component attachment system is secured to routing modules.

As described herein, embodiments of the present disclosure provideraceway systems 200 that are secured to existing structural attachmentlocations within the internal cabin 130. In at least one embodiment, theexisting structural attachment locations are those that would securestowage bin assemblies inside an internal cabin of a commercialaircraft. The raceway systems 200 include routing modules 210 into whichthe transferring components are secured, instead of securing thetransferring components directly to brackets, frames, stringers, and/orthe like. As such, the manufacturing process is vastly improved in thatit is less time- and labor-intensive (both in terms of a factory shopperspective, as well as an engineering definition) as compared to priorknown manufacturing processes for military commercial derived aircraft.The raceway systems 200 provide quick and easy access to wiring andducting during installation, as well as for inspection and maintenance,and future modifications and upgrades.

Embodiments of the present disclosure provide systems and methods forefficiently mounting transferring components (such as electrical wiring,ducting, liquid conduits, and/or the like) within an internal cabin ofan aircraft, such as a military commercial derivative aircraft. Further,embodiments of the present disclosure provide systems and methods thatreduce the time, effort, and cost of designing and securing transferringcomponents within an internal cabin of an aircraft, and reduce a totalmanufacturing time. Further, embodiments of the present disclosureprovide systems and methods that allow for easy and cost-efficientinspection of installed wiring within an aircraft.

While various spatial and directional terms, such as top, bottom, lower,mid, lateral, horizontal, vertical, front and the like may be used todescribe embodiments of the present disclosure, it is understood thatsuch terms are merely used with respect to the orientations shown in thedrawings. The orientations may be inverted, rotated, or otherwisechanged, such that an upper portion is a lower portion, and vice versa,horizontal becomes vertical, and the like.

As used herein, a structure, limitation, or element that is “configuredto” perform a task or operation is particularly structurally formed,constructed, or adapted in a manner corresponding to the task oroperation. For purposes of clarity and the avoidance of doubt, an objectthat is merely capable of being modified to perform the task oroperation is not “configured to” perform the task or operation as usedherein.

It is to be understood that the above description is intended to beillustrative, and not restrictive. For example, the above-describedembodiments (and/or aspects thereof) may be used in combination witheach other. In addition, many modifications may be made to adapt aparticular situation or material to the teachings of the variousembodiments of the disclosure without departing from their scope. Whilethe dimensions and types of materials described herein are intended todefine the parameters of the various embodiments of the disclosure, theembodiments are by no means limiting and are exemplary embodiments. Manyother embodiments will be apparent to those of skill in the art uponreviewing the above description. The scope of the various embodiments ofthe disclosure should, therefore, be determined with reference to theappended claims, along with the full scope of equivalents to which suchclaims are entitled. In the appended claims, the terms “including” and“in which” are used as the plain-English equivalents of the respectiveterms “comprising” and “wherein.” Moreover, the terms “first,” “second,”and “third,” etc. are used merely as labels, and are not intended toimpose numerical requirements on their objects. Further, the limitationsof the following claims are not written in means-plus-function formatand are not intended to be interpreted based on 35 U.S.C. § 112(f),unless and until such claim limitations expressly use the phrase “meansfor” followed by a statement of function void of further structure.

This written description uses examples to disclose the variousembodiments of the disclosure, including the best mode, and also toenable any person skilled in the art to practice the various embodimentsof the disclosure, including making and using any devices or systems andperforming any incorporated methods. The patentable scope of the variousembodiments of the disclosure is defined by the claims, and may includeother examples that occur to those skilled in the art. Such otherexamples are intended to be within the scope of the claims if theexamples have structural elements that do not differ from the literallanguage of the claims, or if the examples include equivalent structuralelements with insubstantial differences from the literal language of theclaims.

The invention claimed is:
 1. A raceway system within an aircraft, theraceway system comprising: a plurality of routing modules that arecoupled together, wherein each of the plurality of routing modulesincludes a main housing that routes one or more transferring componentsto one or more monuments within the aircraft, wherein the main housingcomprises a bottom opening, wherein portions of the one or moretransferring components extend through the bottom opening to couple tothe one or more monuments, and wherein at least one of the plurality ofmodules comprises a door that is pivotally coupled to the main housingproximate to the bottom opening, wherein the door is configured to beselectively moved between an open position and a closed position.
 2. Theraceway system of claim 1, further comprising at least one fixed panelthat extends between at least one of the plurality of modules and theone or more monuments.
 3. The raceway system of claim 1, wherein theplurality of routing modules are outside of a sidewall and ceiling of aninternal cabin of the aircraft.
 4. The raceway system of claim 1,wherein at least one of the plurality of routing modules is positionedabove the one or more monuments.
 5. The raceway system of claim 1,wherein each of the plurality of routing modules is secured to one orboth of at least one frame or at least one stringer by one or morestowage bin mounting supports.
 6. The raceway system of claim 1, whereinone or more of the plurality of routing modules comprises a longitudinalseparating wall that defines a first space and a second space, whereinthe first space and the second space allow different transferringcomponents to be separated from one another.
 7. The raceway system ofclaim 1, wherein each of the plurality of routing modules comprises oneor more transferring component support struts that secure the one ormore transferring components within the main housing.
 8. The racewaysystem of claim 7, wherein the one or more transferring component strutsare secured to one or more lugs within the main housing through one ormore fasteners.
 9. The raceway system of claim 7, wherein the one ormore transferring components are secured to the one or more transferringcomponent support struts before being secured within the main housing.10. The raceway system of claim 1, wherein at least one of the pluralityof routing modules comprises a top opening formed through a top wall.11. A raceway method for an aircraft, the raceway method comprising:providing a plurality of routing modules; coupling the plurality ofrouting modules together within the aircraft; routing one or moretransferring components to one or more monuments within the aircraftthrough main housings of the plurality of routing modules; extendingportions of the one or more transferring components through bottomopenings of the main housings; pivotally coupling at least one door ofat least one of the plurality of modules to at least one of the mainhousings proximate to at least one of the bottom openings, wherein theat least one door is configured to be selectively moved between an openposition and a closed position.
 12. The raceway method of claim 11,further comprising: disposing the plurality of routing modules outsideof a sidewall and ceiling of an internal cabin of the aircraft.
 13. Theraceway method of claim 11, further comprising positioning at least oneof the plurality of routing modules above the one or more monuments. 14.The raceway method of claim 11, further comprising securing each of theplurality of routing modules to one or both of at least one frame or atleast one stringer with one or more stowage bin mounting supports. 15.The raceway method of claim 11, wherein the providing comprisesproviding one or more of the plurality of routing modules with alongitudinal separating wall that defines a first space and a secondspace, wherein the first space and the second space allow differenttransferring components to be separated from one another.
 16. Theraceway method of claim 11, further comprising: securing the one or moretransferring components to one or more transferring component struts;and securing the one or more transferring component struts that arecoupled to the one or more transferring components to one or more lugswithin the main housings.
 17. The raceway method of claim 11, whereinthe providing comprises forming a top opening through a top wall of atleast one of the plurality of routing modules.
 18. An aircraftcomprising: a fuselage defining an internal cabin, wherein the fuselageincludes a plurality of frames and a plurality of stringers connected tothe plurality of frames; one or more monuments within the internalcabin; and a raceway system within the internal cabin, the racewaysystem comprising a plurality of routing modules that are coupledtogether, wherein each of the plurality of routing modules includes amain housing that routes one or more transferring components to the oneor more monuments within the internal cabin, wherein the main housingcomprises a bottom opening, wherein portions of the one or moretransferring components extend through the bottom opening to couple tothe one or more monuments, wherein at least one of the plurality ofmodules comprises a door that is pivotally coupled to the main housingproximate to the bottom opening, wherein the door is configured to beselectively moved between an open position and a closed position,wherein at least one of the plurality of routing modules comprises a topopening formed through a top wall, wherein at least one of the pluralityof routing modules is positioned above the one or more monuments,wherein the plurality of routing modules are outside of a sidewall andceiling of the internal cabin, wherein each of the plurality of routingmodules is secured to at least one of the frames or the stringers by oneor more stowage bin mounting supports, wherein one or more of theplurality of routing modules comprises a longitudinal separating wallthat defines a first space and a second space, wherein the first spaceand the second space allow different transferring components to beseparated from one another, wherein each of the plurality of routingmodules comprises one or more transferring component support struts thatsecure the one or more transferring components within the main housing,wherein the one or more transferring components are secured to the oneor more transferring component support struts before being securedwithin the main housing, and wherein the one or more transferringcomponent struts are secured to one or more lugs within the main housingthrough one or more fasteners.
 19. The raceway system of claim 1,wherein the door comprises one or more door openings that allow at leasta portion of the one or more transferring components to extend throughthe door in the closed position.
 20. The aircraft of claim 18, whereinthe door comprises one or more door openings that allow at least aportion of the one or more transferring components to extend through thedoor in the closed position.